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TECHNICAL PAPERS

Experimental Demonstration of Maximum Mistuned Bladed Disk Forced Response

[+] Author and Article Information
J. A. Kenyon

Air Force Research Laboratory, Propulsion Directorate, Wright-Patterson AFB, OH 45433   e-mail: james.kenyon@wpafb.af.mil

J. H. Griffin

Department of Mechanical Engineering, Carnegie Mellon University, Pittsburgh, PA 15213e-mail: jg9h@andrew.cmu.edu

J. Turbomach 125(4), 673-681 (Dec 01, 2003) (9 pages) doi:10.1115/1.1624847 History: Received December 01, 2002; Revised March 01, 2003; Online December 01, 2003
Copyright © 2003 by ASME
Topics: Disks , Blades , Damping , Waves
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References

Figures

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Optimum mode shape for maximum response
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Test setup for traveling wave forced response test
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Forced response of optimized bladed disk with maximum response
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Forced response of nominally tuned bladed disk
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Fit of experimental transfer functions to frequency splitting model of MacBain and Whaley 11
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Response distribution comparison between experimental results and MacBain and Whaley 11 model
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Variation of blade 1 response due to small random mistuning
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Lumped parameter model of bladed disk dynamics
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Finite element model of experimental bladed disk
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Experimental setup for measuring natural frequencies, damping, and mode shapes of the bladed disk
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Natural frequencies versus nodal diameters for the tuned bladed disk
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Nominally tuned cosine (113.7 Hz) and sine (114.3 Hz) mode shapes

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